专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08506251B2 Gas turbine blade, manufacturing method therefor, and gas turbine using turbine blade 有权
标题翻译：燃气轮机叶片及其制造方法，以及使用涡轮叶片的燃气轮机
公开(公告)号：US08506251B2
公开(公告)日：2013-08-13
申请号：US13093437
申请日：2011-04-25
申请人： Satoshi Hada , Takahiko Imada , Tomofumi Shintani , Katsutoshi Ooe , Norifumi Hirata , Hiroshi Asano
发明人： Satoshi Hada , Takahiko Imada , Tomofumi Shintani , Katsutoshi Ooe , Norifumi Hirata , Hiroshi Asano
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B23P15/02 , F01D5/18 , Y10T29/49336 , Y10T29/49341
摘要： Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.
摘要翻译：燃气轮机叶片，其简化了设置在涡轮机叶片内部的冷却通道的形成，同时避免了由于形成冷却通道而导致的涡轮机叶片强度和刚度的损失。设置在燃气轮机叶片的内部的冷却通道包括在涡轮机叶片的基部侧沿纵向延伸的多个直的通道状的基本侧的细长孔，多个直的通道状的顶端侧的长孔在涡轮机叶片的前端侧沿长度方向延伸;以及多个连通的中空部，插入在两种类型的长孔之间的连接部分处，以允许两种类型的细长孔彼此连通，并具有较大的十字形横截面积比两个长孔的通道横截面积。连通的中空部分形成为与涡轮叶片的平台部分的位置相匹配。

2. 发明申请

US20110217180A1 GAS TURBINE BLADE, MANUFACTURING METHOD THEREFOR, AND GAS TURBINE USING TURBINE BLADE 审中-公开
标题翻译：气体涡轮叶片，其制造方法和使用涡轮叶片的气体涡轮机
公开(公告)号：US20110217180A1
公开(公告)日：2011-09-08
申请号：US12960970
申请日：2010-12-06
申请人： Satoshi Hada , Takahiko Imada , Tomofumi Shintani , Katsutoshi Ooe , Norifumi Hirata , Hiroshi Asano
发明人： Satoshi Hada , Takahiko Imada , Tomofumi Shintani , Katsutoshi Ooe , Norifumi Hirata , Hiroshi Asano
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/187 , F01D5/225 , F05D2230/11 , F05D2250/70 , Y10T29/49341
摘要： Provided are gas turbine blades in which it is possible to simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. In a gas turbine blade, cooling channels provided in the interior thereof include a plurality of straight channel-like base-side elongated holes that extend in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes that extend in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions that are interposed at connection portions between the two types of elongated holes to individually allow the two types of elongated holes to communicate with each other and that have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. In addition, the communicating hollow portions are formed so as to match the position of a platform portion of the turbine blade.
摘要翻译：提供了一种燃气轮机叶片，其中可以简化设置在涡轮机叶片内部的冷却通道的形成，同时避免由于形成冷却通道而导致的涡轮叶片强度和刚度的损失。在燃气轮机叶片中，设置在其内部的冷却通道包括在涡轮机叶片的基部侧沿纵向方向延伸的多个直的通道状的基侧长孔，在所述涡轮机叶片的前端侧沿长度方向延伸的侧面长孔，以及多个连通的中空部，其插入在所述两种长孔之间的连接部分处，以分别允许两种类型的长孔与并且具有比两个细长孔的通道横截面积更大的横截面面积。另外，连通用中空部形成为与涡轮叶片的平台部的位置一致。

3. 发明申请

US20110217181A1 GAS TURBINE BLADE, MANUFACTURING METHOD THEREFOR, AND GAS TURBINE USING TURBINE BLADE 有权
标题翻译：气体涡轮叶片，其制造方法和使用涡轮叶片的气体涡轮机
公开(公告)号：US20110217181A1
公开(公告)日：2011-09-08
申请号：US13093437
申请日：2011-04-25
申请人： Satoshi Hada , Takahiko Imada , Tomofumi Shintani , Katsutoshi Ooe , Norifumi Hirata , Hiroshi Asano
发明人： Satoshi Hada , Takahiko Imada , Tomofumi Shintani , Katsutoshi Ooe , Norifumi Hirata , Hiroshi Asano
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/187 , B23P15/02 , F01D5/18 , Y10T29/49336 , Y10T29/49341
摘要： Provided are gas turbine blades in which it is possible to simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. In a gas turbine blade (41), cooling channels (410) provided in the interior thereof include a plurality of straight channel-like base-side elongated holes (401a) that extend in a longitudinal direction at a base side of the turbine blade (41), a plurality of straight channel-like tip-side elongated holes (410b) that extend in a longitudinal direction at a tip side of the turbine blade (41), and a plurality of communicating hollow portions (410c) that are interposed at connection portions between the two types of elongated holes (410a, 410b) to individually allow the two types of elongated holes (410a, 410b) to communicate with each other and that have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes (410a, 410b). In addition, the communicating hollow portions (410c) are formed so as to match the position of a platform portion (413) of the turbine blade (41).
摘要翻译：提供了一种燃气轮机叶片，其中可以简化设置在涡轮机叶片内部的冷却通道的形成，同时避免由于形成冷却通道而导致的涡轮叶片强度和刚度的损失。在燃气轮机叶片（41）中，设置在其内部的冷却通道（410）包括在涡轮机叶片的基部侧沿长度方向延伸的多个直通道状的基侧长孔（401a） 41），在所述涡轮叶片（41）的前端侧沿长度方向延伸的多个直线状的前端侧长孔（410b），以及多个连通用的中空部（410c），其位于两个类型的细长孔（410a，410b）之间的连接部分分别允许两种类型的细长孔（410a，410b）彼此连通并且具有比两者的通道横截面积更大的横截面面积细长孔（410a，410b）。另外，连通用中空部410c形成为与涡轮叶片（41）的平台部（413）的位置一致。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式